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Prognostics and system Health Management Conference (PHM-Qingdao)

作者： Jun Zhan Jie Zeng Chao Xiang Jinpeng Cui Cheng Zeng Linfeng Zhu Mingyu Lu State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics Nanjing China Aviation key laboratory of science and technology on aero electromechanical system integration Nanjing engineering institute of aircraft system jincheng AVIC Nanjing China Changping District Xiaotangshan Future Science and Technology City COMAC Beijing Aircraft Technology Research Institute Beijing China

ISBN: (数字)9798350354010

ISBN: (纸本)9798350354027

The aircraft wing structure shape reconstruction method based on discrete strain information not only provides data support for the digital collaborative health monitoring and prediction technology of wing structure but also helps to improve the aerodynamic shape and flight quality of the aircraft, achieve structural stealth, and enhance the pointing accuracy of the on-board conformal antenna. As result, a wing skin panel shape reconstruction method based on the principle of tomographic imaging and strain information perception is proposed. According to the idea of tomographic imaging, a “non-intrusive” layout form that only requires sensors to be arranged on the periphery of the monitoring area is designed, breaking through the limitation that sensors can not be arranged in the monitoring area under special working conditions. A method for constructing the deflection shape function of the wing skin panel based on the concept of synthetic curvature is proposed, solving the problem of error accumulation and elimination of deformation inversion at non-monitoring points of the measured structure caused by the uncertainty of the limited discrete layout of sensors and the choice of interpolation fitting method. On this basis, a model deformation monitoring and inversion system for wing skin panel based on fiber optic grating sensors is constructed. The experimental results show that under the single-end fixed bending and torsion working condition, the average relative error of the panel model shape reconstruction is 4.17%. Under the double-end fixed double-concentrated load working condition, the average relative error of the shape reconstruction is 8.07%. The wing deformation distribution information reconstructed by the method proposed in this paper can be mapped onto the virtual twin model of the wing, providing technical support for the safety assessment, early warning, and on-condition maintenance of the entire service life of key structures of the aircraft.

关键词： Employee welfare Shape Deformation Layout Imaging Sensors Aircraft Monitoring Image reconstruction Strain

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Design and Analysis of Dual Three-Phase Winding PMSM for Integrated EMA 4

Design and Analysis of Dual Three-Phase Winding PMSM for Int...

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4th IEEE China International Electrical and Energy Conference, CIEEC 2021

作者： Bi, Ying Liu, Qianqian Zhu, Shushu Liu, Chuang Wang, Kai Hu, Yaohua Nanjing University of Aeronautics and Astronautics Department of Electrical Engineering Nanjing China Nanjing Engineering Institute of Aircraft Systems Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (纸本)9781728171494

In modern aerospace electromechanical actuators (EMA), the integrated structure has brought many advantages, such as reducing system components and system volume, etc. In this paper, the design of dual three-phase winding permanent magnet synchronous machine (PMSM) for an integrated EMA is addressed. The motor adopts slot pole combination of 12/10 because of a high winding factor and utilization. The motor is integrated with the EMA system, so the size of it is strictly restricted. Under the condition of limited size, the most suitable stator split ratio is found by analytical calculation and then verified through finite element simulation. Then through the analysis and comparison of three winding configurations, the double-layer winding phase shift 180 degree is selected. Finally, in the case of considering the eddy current loss on the rotor, the optimal design is carried out to obtain the optimal output torque and reduce the torque ripple. © 2021 IEEE.

关键词： electromechanical actuators

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Hydraulic piston pump in civil aircraft: Current status, future directions and critical technologies

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Chinese Journal of aeronautics 2020年第1期33卷 16-30页

作者： Shengrong GUO Jinhua CHEN Yueliang LU Yan WANG Hongkang DONG Nanjing Engineer Institute of Aircraft System Jincheng AVICNanjing 211100China Aviation Science and Technology Key Laboratory of Aero Electromechanical System Integration Nanjing 211100China School of Transportation Science and Engineering Beihang UniversityBeijing 100083China

The piston pump is the key power component in the civil aircraft hydraulic system,and the most common pump used in the aviation field is the pressure compensated variable displacement *** this review paper,a basic introduction to the civil aircraft piston pump is presented,including the classification,structure,working principle,design features,and achievements by some research ***,the future directions of the aircraft pump are reported from various ***,the critical technologies are analyzed and summarized in detail from six thrust areas:friction couples,noise reduction,inlet boost,thermal management,fault diagnosis and health management,and mechanical ***,the challenges and limitations of the research on the aircraft pump are discussed to provide valuable insight for future scholars.

关键词： Civil aircraft Engine driven pump High pressure Inlet boost Intelligent control Lubricating gaps Piston pumps Pulsation reduction

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A bellows booster device for EHA

A bellows booster device for EHA

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CSAA/IET International Conference on Aircraft Utility systems 2020, AUS 2020

作者： Le, Yang AVIC NEIAS Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration

ISBN: (纸本)9781839535635

This paper describes several booster devices commonly applied in the aviation field, analyzes their characteristics, and proposes a scheme for bellows-based gas booster devices according to EHA's requirements on booster devices. By means of theoretical and simulation analysis according to the EHA index, design related parameters for the bellows and develop principle prototype. Verify the feasibility of the bellows gas boosting scheme and the effectiveness of the design method through conducting relevant verification tests on the prototype, so as to support the application of the bellows booster device on EHA. © 2020 Institution of Engineering and technology. All rights reserved.

关键词： Bellows

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GPIO Based Iterative Learning Control for Manipulators with Time-Varying Disturbances

GPIO Based Iterative Learning Control for Manipulators with ...

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第42届中国控制会议

作者： Huangyuwei Lu Zuo Wang Jiankun Sun Xi Xiao Shihua Li School of Automation Southeast University Key Laboratory of Measurement and Control of Complex systems of Engineering Ministry of Education Shenzhen Research Institute Southeast University School of Artificial Intelligence and Automation Huazhong University of Science and Technology Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration

To improve the disturbance rejection ability and repetitive tracking accuracy of manipulators,a composite iterative learning control(ILC) scheme via generalized proportional integral observer(GPIO) is proposed.A high-order polynomial is first employed to model the time-varying disturbances that include unmodeled dynamics,parameter uncertainties and load fluctuations.A GPIO is then designed to estimate the disturbances and high-order time *** introducing estimations into a PD-type ILC at each iteration,a composite control scheme is obtained,such that the undesirable influence of time-varying disturbances can be effectively attenuated in the repetitive tracking process of *** this paper,the rigorous stability analysis of the closed-loop system is presented to guarantee that the tracking error exponentially converges to zero as the iteration number tends to *** effectiveness of the proposed control scheme is finally verified by simulation results.

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Research on Failure Cause Analysis Method Based on Aircraft Maintenance Records 6th

Research on Failure Cause Analysis Method Based on Aircraft ...

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6th China aeronautical science and technology Conference, CASTC 2023

作者： Jiang, Fan Jia, Baohui Wang, Jinglin Zheng, Guo Aviation Key Laboratory of Science and Technology on Fault Diagnosis and Health Management Shanghai201601 China AVIC United Technology Center for Basic Research on Aircraft System Fault Diagnosis and Health Management Shanghai201601 China AVIC Shanghai Aero Measurement and Controlling Research Institute Shanghai201601 China School of Transportation Science and Engineering Civil Aviation University of China Tianjin300300 China

ISBN: (纸本)9789819988631

Due to the accumulation of a large amount of maintenance text information recorded by maintenance personnel based on experience in aircraft maintenance, due to its strong professionalism and diverse expression methods, intelligent analysis has not yet been achieved, making it difficult to fully utilize these data. In response to this issue, this article proposes an aircraft maintenance record analysis method based on the ALBERT-TextCNN model, which solves the fault causes to assist maintenance personnel in correct troubleshooting work. Firstly, the vectorization representation of the preprocessed text and the preliminary feature extraction are performed by using ALBERT;Secondly, the TextCNN model is used to extract deeper features to improve the accuracy of model analysis;Finally, compared with other commonly used text analysis models, the results show that the method used in this article can accurately analyze the causes of faults in aircraft maintenance records, effectively improving the accuracy and speed of analysis. © 2024, Chinese Society of aeronautics and Astronautics.

关键词： Maintenance

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A Capacitance Matrix Expansion Method for Parasitic Capacitance Extraction of Excitation Winding 4

A Capacitance Matrix Expansion Method for Parasitic Capacita...

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4th IEEE Student Conference on Electric Machines and systems, SCEMS 2021

作者： Zezhong, Chen Renhua, Jiang Shushu, Zhu Yaohua, Hu Nanjing University of Aeronautics and Astronautics College of Automation Engineering Nanjing China Avic Leihua Electronic Technology Research Institute Wuxi China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (纸本)9781665436816

The excitation voltage regulator is connected to the excitation winding of the generator to regulate the output power of the generator. The excitation winding is multicircuit winding with multi layers and multi turns. The parasitic capacitance is significant, and it leads to some problems, such as current overshooting and switching losses of the excitation voltage regulator. Therefore, the extraction of the parasitic capacitance of the excitation winding is necessary. A capacitance matrix expansion method is proposed in this paper. The matrix of the parasitic capacitance of the excitation winding is obtained. Due to the symmetric arrangement of the excitation winding, the capacitance matrix can be divided into many parts. The capacitance values of each part approach to a constant which is called the typical capacitance value. The full capacitance matrix is deduced according to the typical capacitance values. After the full capacitance matrix being transformed and simplified, the lumped parasitic capacitance of the excitation winding can be extracted. This method can both take the most advantage of the flexibility of FEA and avoid the unaffordable hardware requirement when extracting the parasitic capacitance of the multicircuit windings. The simulations and experiments are performed for the validation of this method. © 2021 IEEE.

关键词： Voltage regulators

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Numerical simulation and experimental research on Taylor Couette flow characteristics in air gap of aviation motor

Numerical simulation and experimental research on Taylor Cou...

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CSAA/IET International Conference on Aircraft Utility systems (AUS 2024)

作者： Hui Ma Shuyue Liang Hongbo Zhan Lin Qi Weijian Chen Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration No.33 Shuige Road Nanjing People's Republic of China Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Areonautics and Astronautics No.29 Yudao Street Nanjing People's Republic of China

ISBN: (数字)9781837242108

A test bench with PIV technology was built and visualization research on Taylor vortex between concentric rotating cylinders was carried out to explore the flow morphology within the annular gap by changing the rotational speed of the inner cylinder. The numerical method and accuracy were verified by experiments. The selected turbulence model was then applied for numerical simulation of the Taylor Couette flow in a simplified air gap model of an aviation motor with smooth inner and outer walls. The Taylor Couette flow characteristics in the air gap under varying rotational speed were studied, and simulation results were given for flow with axial flow and without axial flow.

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Measurement of aerodynamic heating of micro-scale rotational shearing flow and its heat flux identification

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Chinese Journal of aeronautics 2025年第4期 74-94页

作者： Yuan LIU Yuanwei LYU Jingyang ZHANG Chunyang LI Jingzhou ZHANG Zhongwen HUANG College of Astronautics Nanjing University of Aeronautics and Astronautics Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics Key Laboratory of Thermal Management and Energy Utilization of Aircraft

This study conducted the experimental investigation of aerodynamic heating of Micro-scale Rotational Shearing Flow with Axial Limited-Length（MRSFALL）. The temperature riseof the stator is captured by the high response thermocouples. The eccentricity ratio and clearanceheight are guaranteed by means of instantaneous trajectory and torsion monitoring of the *** result shows that the maximum temperature rise takes place upstream of the minimum clear-ance height along circumferential direction. The distribution of temperature rise presents asymmet-ric curve along axial direction, and peak value occurs near the dimensionless axial position of-0.18. The effect of aerodynamic heating becomes notable as the rotational speed is larger than3 × 10～4r/min. The effect of end leakage and the viscous dissipation have great impact on temper-ature rise of MRSFALL. More specially, the peak value of temperature rise at dimensionless clear-ance height of 0.008 0 is larger than the case at dimensionless clearance height of 0.004 ***, when the eccentricity ratio is too large, the viscous dissipation is induced, and theadditional temperature rise is achieved. The heat flux identification of shear flow has been realizedby Sequential Function Specification Method（SFSM） and its estimation of thermal load has been given. The heat flux induced by the aerodynamic heating in this study varies from 950 W/m2to1 330 W/m2.

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Open-circuit Fault Diagnosis Strategy for Partial Energy Electric Pump system Based on Grey Prediction Theory

Open-circuit Fault Diagnosis Strategy for Partial Energy Ele...

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International Conference on Electrical Machines and systems (ICEMS)

作者： Shirui Yang Xuefeng Jiang Zhijian Wei Jingyu Zhou Kaiwen Wang Zhenmao Han School of Automation Nanjing University of Science and Technology Nanjing China Aero Electromechanical System Aviation Key Laboratory of Science and Technology Nanjing China

ISBN: (数字)9781665493024

ISBN: (纸本)9781665493031

As the core component of the hydraulic system of the multi electric aircraft, the local energy electric pump determines the performance of the hydraulic servo device. Replace the traditional engine pump source hydraulic system to achieve the purpose of saving cost, improving efficiency, reducing weight and volume. Partial electro-hydraulic energy system refers to the highly integrated pump source system and hydraulic transmission system driven by electricity, which are installed near users in the form of independent components to provide power source for users’ actions. Partial energy electric pump system with Fault-tolerant permanent motor (FTPMM) offers the advantages of high-power density, small volume, small torque ripple and fault-tolerance. In this paper, a winding open circuit fault diagnosis strategy for partial energy electric pump system based on grey prediction theory is proposed. The Grey prediction method only needs to collect less motor current data, uses Grey Model to estimate and predict the change rule of the system, which has the advantages of fast diagnosis speed and high diagnostic accuracy under load mutation. Meanwhile, the misjudgment due to load mutation can be avoided effectively.

关键词： Fault diagnosis Fault tolerance Fault tolerant systems Pumps Hydraulic systems Prediction theory Predictive models

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